Helicopter gearbox auxiliary cooling system

Abstract

A cooling system using one or more heat pipes rotating about a central axis to transfer heat energy from one medium to another. The heat pipes are oriented within a rotating member such that the axis of the heat pipe is non-coaxial with that of a central axis of the rotating member. Centrifugal forces are used to assist the movement of the working fluid within the heat pipe. The cooling system also includes heat pipes associated with a planetary carrier assembly and supplemental heat exchangers for use in aircraft and other machinery.

What is claimed is: 
     
       1. A system for transferring heat, comprising:
 a mandrel assembly, having:
 a rotating body defining a central axis, the body having a first end and a second end; 
 a channel formed within the rotating body between the first end and the second end, the channel being angled with respect to the central axis in a non-coaxial relationship; and 
 a heat pipe configured to transfer heat from the first end to the second end as the body rotates about the central axis, the heat pipe located within the channel; 
 
 a planetary carrier assembly having:
 a second heat pipe integrated into a planetary pinion, the planetary carrier assembly being configured to engage a main rotor mast of an aircraft and rotate about a pinion axis; 
 wherein the second heat pipe is configured to transfer heat energy from the planetary pinion to a convective heat exchanger in communication with a convection area; and 
 wherein centrifugal forces assist in the movement of working fluid within the heat pipe as the rotating body is rotated. 
 
 
     
     
       2. The system of  claim 1 , wherein the heat pipe is a rotating heat pipe. 
     
     
       3. The system of  claim 1 , wherein the heat pipe has parallel internal walls. 
     
     
       4. The system of  claim 3 , wherein the heat pipe uses a wick to assist in the movement of the working fluid. 
     
     
       5. The system of  claim 1 , further comprising:
 a condenser fan axially aligned with the central axis and configured to create a heat sink by generating convective air flow over the second end. 
 
     
     
       6. The system of  claim 1 , wherein the heat pipe removes heat from gears and bearings during a loss of lubrication event. 
     
     
       7. A cooling system for removing heat from a transmission of an aircraft, the cooling system comprising:
 a mandrel assembly configured to rotate about a central axis, the mandrel assembly having:
 a rotating body; 
 a channel formed within the rotating body for housing a heat pipe, the heat pipe oriented in a non-coaxial relationship with the central axis; and 
 a condenser configured to generate convective airflow over the heat pipe to condense the working fluid, the condenser having a central aperture for accepting a portion of the rotating body; and 
 
 a planetary carrier assembly having a second heat pipe integrated into a planetary pinion, the planetary carrier assembly being configured to engage a main rotor mast of the aircraft and rotate about a pinion axis; 
 wherein the second heat pipe is configured to transfer heat energy from the planetary pinion to a convective heat exchanger in communication with a convection area; and 
 wherein working fluid within the heat pipe uses centrifugal forces to move between a condenser region to an evaporator region of the heat pipe as the rotating body is rotated. 
 
     
     
       8. The cooling system of  claim 7 , wherein the cooling system is configured to remove heat from the transmission of the aircraft independent of a primary lubrication system. 
     
     
       9. The cooling system of  claim 7 , wherein the cooling system is configured to remove heat from the transmission of the aircraft during a loss of lubrication event sufficient to prevent failure of the transmission of the aircraft for a selected duration. 
     
     
       10. The cooling system of  claim 7 , further comprising a third heat pipe embedded within a housing of the transmission. 
     
     
       11. The cooling system of  claim 7 , further comprising:
 a supplemental heat exchanger configured to penetrate a housing of the transmission, the supplemental heat exchanger using a second heat pipe to transfer heat energy. 
 
     
     
       12. The cooling system of  claim 7 , wherein the cooling system maintains manageable flight operations of the aircraft for a selected duration during a loss of a lubrication event.